CN103511003A - Control system - Google Patents
Control system Download PDFInfo
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- CN103511003A CN103511003A CN201210220517.2A CN201210220517A CN103511003A CN 103511003 A CN103511003 A CN 103511003A CN 201210220517 A CN201210220517 A CN 201210220517A CN 103511003 A CN103511003 A CN 103511003A
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- control system
- blade
- housing
- baffle plate
- driving mechanism
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Abstract
A control system is used in a gas turbine engine, and comprises a shaft, a blade, a shell, a drive mechanism, a baffle, a sensor and a controller. The shaft extends longitudinally; the blade is installed on the shaft and extends outwards and longitudinally to form a blade tip; the shell surrounds the blade; the drive mechanism is fixed to the shell; the baffle can be driven to be connected with the drive mechanism, and an interval is limited between the baffle and the blade tip of the blade; the sensor is arranged on one of the blade, the shell, the drive mechanism and the baffle so as to detect the interval; the controller is in coupling with the sensor and the drive mechanism and responds to the interval detected by the sensor to control the drive mechanism to drive the baffle, and then the interval is adjusted.
Description
Technical field
The present invention relates to control system, relate in particular to the control system of controlling turbine blade-tip gap.
Background technique
Motor is along with thrust adjustment and outside air temperature varies and be operated in different gas flow temperature states, and because the rates of thermal expansion of rotor and casing is different, the gap of blade tip and casing also changes with engine behavior.Tip clearance has material impact to the fuel consumption rate of the efficiency of turbine and motor.Tip clearance increases, and working fluid will increase from the leakage rate of tip clearance, increases leakage rate and can reduce turbine efficiency and the fuel consumption rate of motor is increased.The research of associated mechanisms is found: 1% of the every increase length of blade of turbine blade-tip gap, Efficiency Decreasing 1.5%; The every reduction by 1% of efficiency, oil consumption rate approximately increases by 2%.In addition, the deterioration of tip clearance also can cause the generation of surge, threatens the Security of motor.
In order to prevent, because tip clearance changes the unfavorable effect of bringing, need to controlling the tip clearance of rotor part.The controlling method of turbine blade-tip gap can be divided into two kinds: active gap control and passive gap control.The Large Civil Aircraft motor of international mainstream has all adopted initiatively gap control technology at present.For example, CFM56 motor adopts initiatively gap control of high-pressure turbine.This system is used two strands of air-flows from high-pressure compressor, controls the proportions of ingredients of cooling air volume and two kinds of air-flows by active gap control valve.According to the requirement of regulating radial clearance, the cooling-air that attracts different temperatures under different working staties carries out cooling or heats casing, and guarantee has less tip clearance in cruising.
Tip clearance measuring transducer is one of key technology of initiatively gap control, both at home and abroad all using it as research emphasis.More conventional tip clearance measuring transducer can be divided into microwave type, condenser type and optical fiber type etc. at present, US National Aeronautics and Space Administration's (National Aeronautics and Space Administration is called for short NASA) adopts microwave type sensor to carry out tip clearance and measures test; Group of Aérospatiale Matra is used capacitive transducer to measure tip clearance on its TP400 motor; The high frequency carrier electric capacity amplitude modulation tip clearance of China is measured tentatively industrialized production of sensing device.
Being applied at present active gap control on motor substantially adopts and casing is carried out to cooling or heating controls its swell increment.But because expansion and the contraction of casing needs certain response time, this method response is slower.
In order to overcome the shortcoming of above-mentioned low-response, the present invention proposes a kind of mechanical type active clearance control system of fast and reliable.
Summary of the invention
The present invention proposes a kind of type aeroengine turbine blade tip gap active control system, can improve turbine working efficiency.This system critical piece is mechanical type actuator and sensor, and the main feature of this system is: adopt sensor to measure in real time tip clearance parameter and go out tip clearance by airborne computer computational analysis; Adopt mechanical type actuator according to the real-time measuring data of sensor, tip clearance to be adjusted.
Sensor in this control system has advantages of real-time measurement, response fast; Mechanical type actuator has advantages of reliable, quick response, is easy to safeguard.
Particularly, the invention discloses a kind of control system for gas turbine engine, described control system comprises:
Axle, it longitudinally extends;
Blade, it is arranged on described axle, and radially stretches out and form blade tip;
Housing, it surrounds described blade;
Baffle plate, the blade tip of itself and described blade limits gap;
Driving mechanism, it is fixed on described housing, and described driving mechanism connects and drives described baffle plate to radially move;
Sensor, it is arranged in one of them of described blade, housing, driving mechanism and baffle plate for detection of described gap;
Controller, regulates described gap to control described driving mechanism to the driving of described baffle plate thereby itself and described sensor and described driving mechanism couple and respond the gap that described sensor detects.
Preferably, described baffle plate is a circular plate washer.Selectively, described baffle plate is polylith curved baffle, and described polylith curved baffle upwards forms circular in week.
Particularly, the number of the corresponding described curved baffle of the number of described driving mechanism and arranging.
Particularly, described sensor is arranged between two curved baffles adjacent one another are.
Particularly, described driving mechanism comprises power source, the rotating component being driven by described power source and the leading screw being at one end threaded with described rotating component, wherein, described rotating component is pivotally connected on described housing, and the other end of described leading screw is connected to described baffle plate.
Preferably, between described rotating component and described housing, be also furnished with the link with described housing and described rotating component sliding friction.
More preferably, described link is ball.
Preferably, between described housing and described baffle plate, be also furnished with the link with described housing and described baffle plate sliding friction.
More preferably, described link is roller.
Particularly, described controller is airborne computer.
Particularly, described blade is compressor stator vanes.
Selectively, described blade is turbine rotor blade.
Control system of the present invention can respond fast and be reliable and stable, and this system applies, in active gap control, can be effectively reduced to turbine blade-tip gap, improves turbine efficiency.
Accompanying drawing explanation
In order to explain the present invention, its illustrative embodiments will be described with reference to the drawings hereinafter, in accompanying drawing:
Fig. 1 schematically shows the schematic diagram when baffle plate cross section of control system during in the first state;
Fig. 2 schematically shows the schematic diagram when baffle plate cross section of control system during in the second state;
Fig. 3 schematically shows the partial enlarged drawing of control system;
Fig. 4 schematically shows the schematic diagram of control system circumferential arrangement;
Fig. 5 schematically shows the skeleton diagram of control system.
Wherein, in figure, 1 represents housing, and 2 represent blade, and 3 represent baffle plate, and 4 represent leading screw, and 5 represent rotating component, and 6 represent ball, and 7 represent roller, and 8 represent sensor.
Similar features in different figure is indicated by similar reference character.
Embodiment
As Figure 1-Figure 4, a control system for gas turbine engine, it comprise longitudinal extension axle, be arranged on blade 2 on axle, circumferentially upper around this blade 2 with surround blade 2 toroidal shell 1, be fixedly mounted on driving mechanism 9 on housing 1, can drive the baffle plate 3 and sensor 8 and the controller 10 that are connected to driving mechanism 9.Wherein, blade 2 has blade root and blade tip, thereby blade root is combined blade 2 is fixed on axle by the tongue-and-groove on tenon portion and axle, blade tip and be connected between the baffle plate 3 on housing 1 and be limited with gap.The two ends on the top of housing 1 are upwards outward extended with mounting flange in week respectively, and for following rotating component 5 is installed, the two ends of the bottom of housing 1 guide rib that extended internally diametrically respectively, for guide baffle plate 3 movement diametrically.Those skilled in the art should be appreciated that the concrete structure of mounting flange and guide rib is not determinate, as long as baffle plate can be arranged on to other structures that also can move diametrically on housing, is all fine.For example, as substituting of guide rib, the bottom of housing can be provided with to groove, accordingly, baffle plate be provided with to the projection being fitted to slidably in groove simultaneously.
As shown in Figure 4, in preferrred embodiment of the present invention, this baffle plate 3 is comprised of polylith curved baffle, and these curved baffles upwards form circular in week.Accordingly, the number of this driving mechanism 9 equates with the number of these curved baffles 3,, is six that is, by this, can to every curved baffle 3, drive in man-to-man mode.Sensor 8 is arranged between two curved baffles 3 adjacent one another are.The benefit that each curved baffle 3 is carried out driving is separately, can in the situation that disalignment appears in blade 2, along circumferential, guarantee that the gap width between each curved baffle 3 and the blade tip of blade 2 is consistent.Those of ordinary skill in the art should be appreciated that the number of this driving mechanism can be less than the number of curved baffle or be only one, can to several curved baffles or whole curved baffle, drive with a driving mechanism like this.
According to preferrred embodiment of the present invention, driving mechanism comprises power source (not shown), rotating component 5 and leading screw 4, wherein power source can be motor, its power can come from the generator of aircraft, rotating component 5 is rotatably installed on the mounting flange of housing 1 and rotates by the driving of power source, on rotating component 5, also have tapped through hole, one end of leading screw 4 is rotatably connected on the other end on the tapped through hole of rotating component 5 and is fixedly attached on curved baffle 3.Can between rotating component 5 and housing 1, be provided with the link such as ball 6, like this, when rotating component 5 is when housing 1 rotates, this link respectively with rotating component 5, housing 1 sliding friction.For the relative housing 1 of curved baffle 3 is slided more swimmingly, a plurality of links such as roller 7 can be set between housing 1 and curved baffle 3, like this, when curved baffle 3 is when housing 1 moves diametrically, these links respectively with housing 1 and curved baffle 3 sliding frictions.
In preferrred embodiment of the present invention, sensor 8 is arranged on housing 1.Together with controller 10, sensor 8 and driving mechanism 9 are coupled in the mode being electrically connected to, the sensed data of sensor 8 is passed to controller 10, and controller 10 is controlled driving mechanism 9 by these sensed data again.Wherein, controller 10 is airborne computer.Those skilled in the art should be appreciated that the position that is mounted of sensor can be arbitrarily, that is, can be arranged on blade, also can be arranged on housing, can also be arranged on driving mechanism or baffle plate, as long as can meet mounting design requirement.
In conjunction with Fig. 5, when gas turbine engine is worked, each sensor 8 is all monitored the gap between every curved baffle 3 and housing 1 in real time, and this gap width is sent to controller 10 as Δ 1, controller 10 calculates the gap width Δ 2 allowing between every curved baffle 3 and housing 1 according to the current working state of motor, and Δ 1 and Δ 2 are compared, if Δ 1 is greater than Δ 2, to driving mechanism 9, send instruction so that driving mechanism 9 drives curved baffle 3 to move radially and the position of housing 1 at a distance of Δ 2.When above-mentioned driving mechanism 9 start, rotating component 5 rotates relative to leading screw 4, meanwhile, thereby curved baffle 3 away from the mounting flange of housing 1 by curved baffle 3 more approach blade 2 blade tip so that gap width diminish.Control algorithm method as for controller 10, also have a lot, for example, curved baffle that can prestor type motor (comprises Turbine Blade Temperature Field, case temperature, working time, flying height etc.) under each working state in controller and the gap width between blade tip, then the real time data sending according to sensor is compared, and then regulates.Because concrete controlling method does not belong to emphasis of the present invention, therefore do not repeat them here.
This control system can be the control system of controlling for turbine blade tip clearance, and particularly, blade can be turbine rotor blade, and housing can be turbine casing.Selectively, this control system can be the control system of the tip clearance control for compressor stator vanes, and particularly, blade can be compressor stator vanes, and housing can be compressor casing.
The present invention is limited to the illustrative embodiments presenting in specification and accompanying drawing never in any form.Within all combinations of the mode of execution that illustrates and describe (part) are interpreted as clearly and are incorporated to this specification and be interpreted as and fall within the scope of the present invention clearly.And in the scope of the present invention of summarizing as claims, a lot of distortion are possible.In addition, any reference mark in claims should be configured to limit the scope of the invention.
Claims (13)
1. a control system, it is for gas turbine engine, and described control system comprises:
Axle, it longitudinally extends;
Blade, it is arranged on described axle, and radially stretches out and form blade tip;
Housing, it surrounds described blade;
Baffle plate, the blade tip of itself and described blade limits gap;
Driving mechanism, it is fixed on described housing, and described driving mechanism connects and drives described baffle plate to radially move;
Sensor, it is arranged in one of them of described blade, housing, driving mechanism and baffle plate for detection of described gap;
Controller, regulates described gap to control described driving mechanism to the driving of described baffle plate thereby itself and described sensor and described driving mechanism couple and respond the gap that described sensor detects.
2. control system according to claim 1, is characterized in that, described baffle plate is a circular plate washer.
3. control system according to claim 1, is characterized in that, described baffle plate is polylith curved baffle, and described polylith curved baffle upwards forms circular in week.
4. control system according to claim 3, is characterized in that, the number of the corresponding described curved baffle of the number of described driving mechanism and arranging.
5. control system according to claim 3, is characterized in that, described sensor is arranged between two curved baffles adjacent one another are.
6. control system according to claim 1, it is characterized in that, described driving mechanism comprises power source, the rotating component being driven by described power source and the leading screw being at one end threaded with described rotating component, wherein, described rotating component is pivotally connected on described housing, and the other end of described leading screw is connected to described baffle plate.
7. control system according to claim 6, is characterized in that, is also furnished with the link with described housing and described rotating component sliding friction between described rotating component and described housing.
8. control system according to claim 7, is characterized in that, described link is ball.
9. according to the control system described in claim 1 or 6, it is characterized in that, between described housing and described baffle plate, be also furnished with the link with described housing and described baffle plate sliding friction.
10. control system according to claim 9, is characterized in that, described link is roller.
11. according to the control system described in claim 1-8 any one, it is characterized in that, described controller is airborne computer.
12. according to the control system described in claim 1-8 any one, it is characterized in that, described blade is compressor stator vanes.
13. according to the control system described in claim 1-8 any one, it is characterized in that, described blade is turbine rotor blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210220517.2A CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210220517.2A CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103511003A true CN103511003A (en) | 2014-01-15 |
| CN103511003B CN103511003B (en) | 2015-12-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210220517.2A Active CN103511003B (en) | 2012-06-28 | 2012-06-28 | Control system |
Country Status (1)
| Country | Link |
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| CN (1) | CN103511003B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111963470A (en) * | 2020-08-07 | 2020-11-20 | 中国北方发动机研究所(天津) | Turbocharger compressor clearance control device |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2099515A (en) * | 1981-05-29 | 1982-12-08 | Rolls Royce | Shroud clearance control on a gas turbine engine |
| US4878821A (en) * | 1987-02-11 | 1989-11-07 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Detachable anti-rupture ring for the housing of a turbo power plant |
| US5054997A (en) * | 1989-11-22 | 1991-10-08 | General Electric Company | Blade tip clearance control apparatus using bellcrank mechanism |
| US5096375A (en) * | 1989-09-08 | 1992-03-17 | General Electric Company | Radial adjustment mechanism for blade tip clearance control apparatus |
| US20020071763A1 (en) * | 2000-12-07 | 2002-06-13 | Herbert Brandl | Device for setting the gap dimension for a turbomachine |
| US20070003411A1 (en) * | 2005-07-02 | 2007-01-04 | Rolls-Royce Plc | Variable displacement turbine liner |
| CN101660431A (en) * | 2008-08-29 | 2010-03-03 | 通用电气公司 | System and method for adjusting clearance in a gas turbine |
| CN101899995A (en) * | 2009-05-26 | 2010-12-01 | 通用电气公司 | The system and method that is used for gap control |
-
2012
- 2012-06-28 CN CN201210220517.2A patent/CN103511003B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2099515A (en) * | 1981-05-29 | 1982-12-08 | Rolls Royce | Shroud clearance control on a gas turbine engine |
| US4878821A (en) * | 1987-02-11 | 1989-11-07 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Detachable anti-rupture ring for the housing of a turbo power plant |
| US5096375A (en) * | 1989-09-08 | 1992-03-17 | General Electric Company | Radial adjustment mechanism for blade tip clearance control apparatus |
| US5054997A (en) * | 1989-11-22 | 1991-10-08 | General Electric Company | Blade tip clearance control apparatus using bellcrank mechanism |
| US20020071763A1 (en) * | 2000-12-07 | 2002-06-13 | Herbert Brandl | Device for setting the gap dimension for a turbomachine |
| US20070003411A1 (en) * | 2005-07-02 | 2007-01-04 | Rolls-Royce Plc | Variable displacement turbine liner |
| CN101660431A (en) * | 2008-08-29 | 2010-03-03 | 通用电气公司 | System and method for adjusting clearance in a gas turbine |
| CN101899995A (en) * | 2009-05-26 | 2010-12-01 | 通用电气公司 | The system and method that is used for gap control |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111963470A (en) * | 2020-08-07 | 2020-11-20 | 中国北方发动机研究所(天津) | Turbocharger compressor clearance control device |
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| Publication number | Publication date |
|---|---|
| CN103511003B (en) | 2015-12-16 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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